JP5485006B2 - Turbine airflow rectifier - Google Patents

Description

  The present invention relates generally to turbine engines and, more particularly, to an air flow rectification system that improves air distribution within an air chamber.

  In various engines, such as turbine engines, fuel and air mixing affects engine performance and emissions. For example, some gas turbine engines incorporate air and fuel using one or more fuel nozzles to promote fuel-air mixing within the combustor. A nozzle may be located at the head end of the turbine and configured to take an air flow and mix with the fuel input. However, the air flow may not be evenly distributed among the plurality of nozzles, resulting in variations in the mixing of fuel and air. Further, in a single nozzle embodiment, the air flow may not be uniform within the nozzle due to the geometry of the turbine combustor head end. Non-uniform flow within the fuel nozzle leads to inadequate mixing with the fuel, reducing the performance and efficiency of the turbine engine. As a result, the air flow entering the head end can cause increased emissions and reduced performance due to the non-uniform flow of air into each nozzle and between multiple nozzles.

US Pat. No. 6,438,959

  Several embodiments of the invention described in the scope of claims of the present application will be summarized. These embodiments do not limit the technical scope of the invention described in the claims, but simply summarize possible forms of the invention. Indeed, the invention is not limited to the embodiments set forth below but encompasses various different embodiments.

  In a first embodiment, the system comprises a turbine engine. The turbine engine includes a combustor. The combustor includes a combustion chamber. The combustor also includes an air chamber. The combustor further includes a partition plate between the combustion chamber and the air chamber. Further, the combustor includes a fuel nozzle that extends through the partition plate. The fuel nozzle has an air inlet in the air chamber and an outlet in the combustion chamber. The combustor also includes an air flow rectifier provided in the air chamber along an air supply path to the air chamber. The air flow rectifier includes a perforated turning vane configured to turn the air flow from the air supply path inward toward the center of the air chamber.

  In a second embodiment, the system comprises an airflow rectifier configured to be mounted in an air chamber separated from a combustion chamber of a turbine combustor. The airflow rectifier comprises a perforated annular wall configured to direct the airflow axially and radially with respect to the turbine combustor axis. Further, the airflow rectifier is configured to uniformly supply an airflow to the air inlet of one or more fuel nozzles.

  In a third embodiment, the system comprises a turbine combustor. The turbine combustor includes a combustion chamber. The turbine combustor also includes a head end upstream of the combustion chamber for the flow of combustion products. The head end includes a fuel nozzle provided at the head end. The fuel nozzle includes an air inlet at a first axial position relative to the longitudinal axis of the turbine combustor. The head end also includes an air flow rectifier provided at the head end. The airflow rectifier is disposed at a second axial position relative to the longitudinal axis. The first axial position is different from the second axial position.

1 is a block diagram of an embodiment of a turbine system having an airflow rectifier. FIG. 2 is a side cross-sectional view of the embodiment of the turbine system shown in FIG. 1 having a combustor having one or more fuel nozzles. FIG. 3 is a cross-sectional side view of an embodiment of a combustor having one or more fuel nozzles shown in FIG. 2 that may be arranged to draw compressed air from a head end region. FIG. 4 is a side cross-sectional view of an embodiment of the head end region enclosed by line 4-4 in FIG. 3, showing compressed air flowing into the head end region. FIG. 4 is another cross-sectional side view of the embodiment of the head end region enclosed by line 4-4 in FIG. 3, showing compressed air flowing into the head end region. FIG. 6 is a cross-sectional front view 6-6 of the exemplary embodiment of the head end region of FIG. 5 showing a uniform distribution of compressed air in the radial direction between the fuel nozzles. FIG. 7 is a partial cross-sectional side view of the exemplary embodiment of one of the fuel nozzles of FIG. 6 taken along arrow 7-7, showing a uniform distribution of compressed air in the axial direction. FIG. 3 is a perspective view of an exemplary embodiment of a divider and airflow rectifier that may be used in the headend region. FIG. 5 is a partial cross-sectional profile of a perforated turning blade of the airflow rectifier shown in FIGS. 3 and 4. 9B is a partial cross-sectional profile of the perforated turning blade of FIG. 9A in which the leading edge of the perforated turning blade is not connected to the outer wall of the head end region. FIG. 9 is a partial cross-sectional profile of a perforated turning blade of the airflow rectifier shown in FIGS. 5 and 8. 9D is a partial cross-sectional profile of the perforated turning vane of FIG. 9C where the leading edge of the perforated turning vane is not connected to the outer wall of the head end region. It is a partial cross-sectional profile of the L-shaped perforated turning blade of an airflow rectifier. 2 is a partial cross-sectional profile of a hook-shaped perforated turning blade of an air flow rectifier. 2 is a partial cross-sectional profile of a curved perforated turning blade of an airflow rectifier. Figure 3 is a partial cross-sectional profile of another curved perforated turning vane of an airflow rectifier. 1 is a perspective view of a portion of an exemplary embodiment of a perforated turning vane. FIG.

  These and other features, aspects and advantages of the present invention may be better understood by reference to the following detailed description taken in conjunction with the drawings in which: Throughout the drawings, like reference numerals are used for like members.

  The following describes one or more specific embodiments of the present invention. In an effort to provide a concise description of these embodiments, all features in an actual implementation may not be described herein. As with any engineering or design project, when developing for implementation, implementation-specific to achieve specific developer goals (such as complying with system and operational constraints) that vary from implementation to implementation It will be clear that many decisions need to be made. Furthermore, while such development efforts may be complex and time consuming, it will be apparent to those of ordinary skill in the art who have access to the disclosure herein only routine design, assembly and manufacture.

  When introducing components of various embodiments of the present invention, what is written in the singular means that there are one or more of the components. The terms “comprising”, “comprising” and “having” are inclusive and mean that there may be additional elements other than the listed components. Examples of operating parameters and / or environmental conditions do not exclude parameters / conditions other than the disclosed embodiments. Furthermore, references to “one embodiment” or “an embodiment” of the present invention do not exclude the presence of other embodiments having the features described in that embodiment.

  As described in detail below, various embodiments of airflow rectifiers and related structures can be used to improve turbine engine performance and reduce emissions. For example, if the disclosed airflow rectifier is placed in the head end region of a gas turbine combustor, the airflow rectifier can improve the distribution and uniformity of the airflow to one or more fuel nozzles. The air flow rectifier improves the uniformity of the air flow between multiple fuel nozzles (when there are two or more fuel nozzles) and at each fuel nozzle (eg, the air flow rectifier around each fuel nozzle). It is configured to improve the uniformity of the incoming air flow.

  For example, airflow rectifier embodiments may include perforated turning vanes, which are annular structures that vary in diameter along the longitudinal axis of the combustor. Specifically, the perforated turning vanes may be convex or concave, and the perforated turning vanes are configured to direct the air flow axially and radially inward and outward along the longitudinal axis of the combustor. By directing air in multiple directions including radial and axial directions, the perforated turning vane breaks up the large flow structure into a small flow structure, thus balancing in the air chamber at the combustor head end Configured to produce an air mass flow.

  In another embodiment, the perforated turning vane may be conical or annular geometry and may be configured to direct the air flow axially and radially within the air chamber. Further, the perforated turning vane may be connected to a perforated cylinder or wall, and the perforated cylinder or wall may be an annular structure configured to direct air radially. When a perforated annular wall or cylinder is used with a perforated turning vane, the flow structure in the air chamber can be broken to evenly distribute the air to one or more fuel nozzles in the air chamber.

  Thus, the improved and balanced flow of air to one or more fuel nozzles can increase the predictability of air and fuel mixing in the combustor and improve performance. In addition, a perforated airflow rectifier that includes a perforated turning vane annular member can improve the flow to individual fuel nozzles by equalizing the airflow entering the fuel nozzles. A perforated airflow rectifier that includes a perforated turning vane annular member can equalize and balance the air distributed to the air chamber at the head end, ensuring a uniform distribution of intake air among multiple fuel nozzles Is done. Thus, the uniform distribution of air between the fuel nozzles improves combustion performance, thereby reducing emissions and improving system efficiency.

  Referring now to FIG. 1 of the drawings, a block diagram of an embodiment of a turbine system 10 is shown. As described in detail below, the disclosed turbine system 10 can use an airflow rectifier to improve the performance of the turbine system 10 and reduce emissions. The turbine system 10 may operate the turbine system 10 using liquid or gas fuel (eg, natural gas and / or hydrogen rich syngas). As shown, a plurality of fuel nozzles 12 take in a fuel supply 14 to mix fuel and air and distribute the air fuel mixture to the combustor 16. The air-fuel mixture is burned in a combustion chamber in the combustor 16 to generate high-temperature pressurized exhaust gas. The combustor 16 sends exhaust gas through the turbine 18 to the exhaust port 20. As exhaust gas passes through the turbine 18, the gas acts on one or more turbine blades to rotate the shaft 22 along the axis of the system 10. As shown, the shaft 22 may be connected to various components of the turbine system 10 (eg, compressor 24). The compressor 24 also includes a moving blade, and the moving blade may be connected to the shaft 22. As the shaft 22 rotates, the blades in the compressor 24 also rotate so that air from the air intake 26 is compressed while passing through the compressor 24 and enters the fuel nozzle 12 and / or combustor 16. The shaft 22 may be connected to the load 28. The load 28 may be a vehicle or a steady load (for example, a generator in a power plant or an aircraft propeller). Of course, the load 28 may include any suitable device that can be powered by the rotational output of the turbine system 10.

  FIG. 2 illustrates a cross-sectional side view of an embodiment of the turbine system 10 schematically illustrated in FIG. The turbine system 10 includes one or more fuel nozzles 12 disposed within one or more combustors 16. In operation, air enters the turbine system 10 through the air intake 26. Air may be pressurized in the compressor 24. The compressed air may then be mixed with gas in the combustor 16 for combustion. For example, a fuel-air mixture from the fuel nozzle 12 may be injected into the combustor 16 at a rate suitable for optimal combustion, emissions, fuel consumption, and power output. High-temperature pressurized exhaust gas is generated by combustion. The hot pressurized exhaust gas then drives one or more blades 30 in the turbine 18 to rotate the shaft 22 and thus the compressor 24 and the load 28. As the turbine blade 30 rotates, the shaft 22 rotates, so that the blade 32 in the compressor 24 sucks and pressurizes the air received by the intake 26.

  As will be described in detail below, embodiments of the turbine system 10 include certain structures and components in the head end of the combustor 16 to improve the flow of air entering the fuel nozzle 12 so that performance is improved. Improved and reduced emissions. For example, an air flow rectifier (including perforated turning vanes) may be disposed in the air flow path leading to the air chamber. Perforated turning vanes allow air to be sent in a uniform and balanced manner, improving the distribution of air entering the fuel nozzle 12 and, as a result, improving the fuel-air mixture ratio and improving the accuracy of the ratio. Rise.

  FIG. 3 is a cross-sectional side view of an embodiment of a combustor 16 having one or more fuel nozzles 12. The fuel nozzle 12 may be arranged to suck in compressed air from the head end region 34. The end cover 36 may include a conduit or path that delivers fuel and / or pressurized gas to the fuel nozzle 12. Compressed air 38 from the compressor 24 flows into the combustor 16 through an annular passage 40 formed between the combustor flow sleeve 42 and the combustor liner 44. The compressed air 38 flows into the head end region 34. The head end region 34 includes a plurality of fuel nozzles 12. In particular, in certain embodiments, the head end region 34 includes a central fuel nozzle 12 that extends through the central longitudinal axis 46 of the head end region 34 and a plurality of exteriors disposed about the central longitudinal axis 46. A fuel nozzle 12 may be provided. However, in other embodiments, the head end region 34 may comprise only one fuel nozzle 12 extending through the central longitudinal axis 46. The particular configuration of the fuel nozzle 12 within the head end region 34 may vary between particular designs.

  In general, however, the compressed air 38 that flows into the head end region 34 may flow into the fuel nozzle 12 through a nozzle inlet flow rectifier having inlet perforations 48. The air inlet perforations 48 may be arranged on a cylindrical wall outside the fuel nozzle 12. As will be described in more detail below, the airflow rectifier 50 provides a large flow structure (eg, a single annular jet) of compressed air 38 when the compressed air 38 is sent to the headend region 34. May break into small fluid structures. Furthermore, the airflow rectifier 50 guides or sends the airflow in a manner that increases the uniformity of the airflow distribution between the different fuel nozzles 12. As a result, the uniformity of the air flow entering each individual fuel nozzle 12 is also improved. Accordingly, the distribution of compressed air 38 may be more uniform and air intake may be balanced among the fuel nozzles 12 in the head end region 34. Compressed air 38 enters fuel nozzle 12 via inlet perforations 48 and then mixes with fuel and flows through internal volume 52 of combustor liner 44 (shown by arrow 54). The mixture of air and fuel flows into the combustion cavity 56. The combustion cavity 56 may function as a combustion zone. The heated combustion gas exiting the combustion cavity 56 flows into the turbine nozzle 58 (indicated by arrow 60) where it is delivered to the turbine 18.

  4 is a cross-sectional side view of an embodiment of the head end region 34 surrounded by line 4-4 in FIG. As shown, the compressed air 38 may enter the head end region 34 or may change direction and enter the inlet perforation 48 of the fuel nozzle 12 (indicated by arrow 62). As described above, the compressed air 38 may be mixed with the fuel and / or the pressurized gas 64 in the fuel nozzle 12. Fuel and / or pressurized gas 64 is introduced into fuel nozzle 12 through conduits and valves through end cover 36. The air / fuel mixture 66 may then be sent from the head end region 34 to the internal volume 52 (shown in FIG. 3) of the combustor liner 44.

As shown in FIG. 4, the compressed air 38 that flows into the head end region 34 may pass through the airflow rectifier 50 before entering the fuel nozzle 12. The airflow rectifier 50 is disposed in the air chamber 68 in the head end region 34. The air chamber 68 may be described as an air flow dump region or an air flow reversal region. This is because the air flow spreads into a larger volume and reverses the direction from the upstream flow direction to the downstream flow direction. As described above, the airflow rectifier 50 may improve the performance of the combustor 16 by ensuring that the compressed air 38 enters the fuel nozzle 12 with increased uniformity. In particular, the air flow rectifier 50 distributes the compressed air 38 uniformly between the fuel nozzles 12 and also distributes the compressed air 38 evenly across the individual nozzle cross sections. In other words, the airflow rectifier 50 provides a uniform flow of compressed air 38 into the inlet perforations 48 of the fuel nozzle 12 so as to evenly distribute the flow of compressed air 38 among the plurality of fuel nozzles 12. It is configured. Specifically, the airflow rectifier 50 is configured to direct the flow of compressed air 38 axially and radially with respect to the central longitudinal axis 46 of the headend region 34. As shown, the airflow rectifier 50 may include two main features that contribute to increasing the compressed air 38 flow. In particular, the airflow rectifier 50 may include a perforated turning vane 70 configured to turn the compressed air 38 toward the center of the air chamber 68. Specifically, the perforated turning vane 70 may gently change the direction of the compressed air 38 toward the inlet perforation 48 of the fuel nozzle 12. For example, certain embodiments of perforated turning vanes 70 typically change the direction of air flow using one or more angled or curved structures. The angle of these structures may be at least greater than 0, 10, 20, 30, 40, 50, 60, 70, or 80 degrees with respect to the longitudinal axis. The perforated turning vane 70 may include a perforated annular wall 72 disposed about the central longitudinal axis 46 of the head end region 34. The perforated annular wall 72 may vary in diameter along the central longitudinal axis 46. For example, as shown in FIG. 4, the perforated annular wall 72 may gradually decrease in diameter from the combustor end 74 to the head end 76 along the central longitudinal axis 46. In certain embodiments, the perforated annular wall 72 may comprise a plurality of conical walls that converge or diverge linearly along the central longitudinal axis 46. For example, as shown in FIG. 4, the perforated annular wall 72 includes a first perforated annular wall 78 and a second perforated wall 80 to which the first perforated annular wall 78 is connected. Also good. As shown, the first perforated annular wall 78 only converges gradually toward the central longitudinal axis 46, while the second perforated wall 80 is aligned with the central longitudinal axis 46. Concentrating more rapidly. Indeed, as will be described in more detail below, the perforated annular wall 72 may have various configurations and arrangements that may enhance the flow of compressed air 38 toward the fuel nozzle 12.

In some embodiments, in addition to the perforated annular wall 72, the airflow rectifier 50 may include a perforated cylinder 82. In essence, the perforated cylinder 82 is an internal perforated annular wall of the airflow rectifier 50 that connects to the perforated annular wall 72 and extends rearward toward the combustor end 74 of the head end region 34. Good. As shown in FIG. 4, the perforated cylinder 82 may constitute a perforated cylindrical wall disposed around the central longitudinal axis 46 of the head end region 34. The perforated cylinder 82 may have a substantially constant diameter along the central longitudinal axis 46. In particular, in some embodiments, the perforated cylinder 82 and the perforated annular wall 72 may be substantially concentric with each other. In general, the perforated cylinder 82 may supplement the perforated annular wall 72 when changing the direction of the compressed air 38 in an optimal manner toward the fuel nozzle 12.

  FIG. 5 is another cross-sectional side view of an embodiment of the head end region 34. As previously described, the compressed air 38 may enter the head end region 34 and flow across the airflow rectifier 50. As shown in FIG. 5, in some embodiments, the airflow rectifier 50 may include only perforated turning vanes 70. As the compressed air 38 flows across the airflow rectifier 50, the compressed air 38 may be sent in both the axial direction 84 and the radial direction 86 relative to the central longitudinal axis 46 of the head end region 34. In general, the compressed air 38 sent in the axial direction 84 concentrates toward the fuel nozzle 12 along the radial circumference of the head end region 34, while the compressed air 38 sent in the radial direction 86. Are more dispersed toward the fuel nozzle 12 located near the central longitudinal axis 46. Thus, the compressed air 38 may be more evenly distributed among the fuel nozzles 12, as opposed to the concentrated concentrated compressed air 38 toward the fuel nozzle 12 near the head end region 34. For example, arrow 88 illustrates compressed air 38 that is more evenly distributed among the plurality of fuel nozzles 12 in headend region 34. In some embodiments, the perforated turning vane 70 may be adjusted for a specific arrangement of fuel nozzles, rectifiers, and the like. For example, adjustment of the perforated turning vane 70 may be made by adjusting the angle, geometry, and length of the perforated turning vane 70 while also adjusting the number, size, and distribution of perforations.

  FIG. 6 is a front cross-sectional view of an exemplary embodiment of the head end region 34 taken along line 6-6 of FIG. 5, showing a radially uniform distribution of compressed air 38 between the fuel nozzles 12. . The head end region 34 may include a plurality of fuel nozzles 12. In particular, in certain embodiments, the head end region 34 includes a centrally located fuel nozzle 90 and a plurality of fuel nozzles 92, 94, radially disposed about the centrally located fuel nozzle 90. 96, 98, and 100 may be provided. As described above, the airflow rectifier 50 is configured so that the compressed air 38 is evenly distributed between the fuel nozzles 90, 92, 94, 96, 98, and 100 and evenly around each individual fuel nozzle. May help to ensure that. For example, the air velocity vector 102 for the centrally located fuel nozzle 90, and the air velocity vectors 104, 106, 108, 110, and 112 for the radially disposed fuel nozzles 92, 94, 96, 98, and 100; And shows how the compressed air 38 can be evenly distributed by the airflow rectifier 50. As shown, the magnitude of the air velocity vectors 102, 104, 106, 108, 110, and 112 are substantially similar for all of the fuel nozzles 90, 92, 94, 96, 98, and 100. There may be. In other words, the air velocity may be substantially the same into each of the fuel nozzles 90, 92, 94, 96, 98, and 100.

  In some cases, without the airflow rectifier 50, the high speeds near the external fuel nozzles 92, 94, 96, 98, and 100 will cause the external fuel nozzles 92, 94, 96, 98, and 100 to run out of air. However, on the other hand, it may tend to be excessively supplied to the fuel nozzle 90 disposed in the center. The air flow rectifier 50 reduces the tangential velocity in the vicinity of the external fuel nozzles 92, 94, 96, 98, and 100, resulting in static around the external fuel nozzles 92, 94, 96, 98, and 100. The pressure increases, allowing a more even distribution of air.

  Also, when airflow rectifier 50 is used, the magnitude of air velocity vectors 102, 104, 106, 108, 110, and 112 for each individual fuel nozzle 90, 92, 94, 96, 98, and 100. May be substantially similar along the circumference of certain fuel nozzles 90, 92, 94, 96, 98, and 100. For example, the magnitudes of the air velocity vectors 104 along the circumference of the radially disposed fuel nozzles 92 may be substantially the same. This is again due, at least in part, to the ability to evenly distribute the compressed air 38 in a way that cannot be done by the airflow rectifier 50.

  In addition, FIG. 7 is a partial cross-sectional side view of the exemplary embodiment of one of the fuel nozzles of FIG. 6 (eg, 92) taken along the line 7-7, showing a uniform distribution of the compressed air 38 in the axial direction. In particular, for fuel nozzle 92, air velocity vectors 114, 116, 118, and 120 are illustrated at a plurality of axial positions along the length of fuel nozzle 92. In particular, the air velocity vector 114 may be near the head end 122 of the fuel nozzle 92 and the air velocity vector 120 may be near the combustor end 124 of the fuel nozzle 92. In other words, the air velocity vector 120 may be closer to where the compressed air 38 enters the head end region 34, while the air velocity vector 114 is closer to where the compressed air 38 enters the head end region 34. It may be far away.

  As shown in FIG. 7, the magnitudes of the air velocity vectors 114, 116, 118, and 120 may all be substantially similar. In other words, the air velocity may be substantially the same at each of the corresponding axial positions. This illustrates how the compressed air 38 can be more evenly distributed axially with respect to the fuel nozzle 92.

  Returning now to FIG. 5, the air chamber 68 in the head end region 34 may be separated from the combustor 16 by a divider 126 (otherwise known as a “cap”). FIG. 8 is a perspective view of an exemplary embodiment of divider plate 126 and airflow rectifier 50. As shown in FIG. 8, the partition plate 126 may include a plurality of openings 128 for accommodating and supporting the fuel nozzle 12. In particular, the opening 128 may be configured to form a seal against a cylindrical wall outside the fuel nozzle 12. In some embodiments, a perforated cylinder 82 associated with the airflow rectifier 50 may be connected to the divider plate 126 as shown. Further, in some embodiments, the fuel nozzle 12 may be disposed between the openings 130 of the subpartition plate 132 to further isolate the air chamber 68 in the head end region 34 from the combustor 16. In some embodiments, a premix assembly may be placed in the space between dividers 126,132.

  As described above, the perforated turning vanes 70 of the air flow rectifier 50 may allow a uniform distribution of the compressed air 38 between the fuel nozzles 12 in the head end region 34. As shown in FIG. 8, the perforated turning blade 70 may have an annular shape whose cross section is substantially constant in the circumferential direction around the shaft 46. However, the specific cross-sectional profile of the annular perforated turning vane 70 may vary. For example, the perforation geometry, distribution, and perforation size may be constant or variable in the axial, radial, and / or circumferential directions relative to the axis 46. In the illustrated embodiment, the perforations 73 on the perforated annular wall 72 are smaller in size and more closely packed together than the perforations 83 on the perforated cylinder 82. Further, the diameter of the perforations 73 is constant, while the diameter of the perforations 83 decreases in the upstream direction. Various other combinations of perforation geometry, distribution, and perforation size may also be implemented.

  9A-9H are partial cross-sectional profile views of an exemplary embodiment of the perforated turning vane 70 of the airflow rectifier 50. FIG. 9A shows a partial cross-sectional profile of the perforated turning vane 70 corresponding to the airflow rectifier 50 shown in FIGS. 3 and 4. Specifically, the illustrated perforated turning blade 70 includes a first perforated annular wall 78 and a second perforated annular wall 80 to which the first perforated annular wall 78 is connected. In the illustrated embodiment, the first perforated annular wall 78 only converges gradually toward the central longitudinal axis 46 of the head end region 34, while the second perforated wall 80 is centered. It converges more rapidly toward the longitudinal axis 46. In general, however, the cross-sectional profile provided by the illustrated embodiment of the perforated turning vane 70 comprises two linearly converging perforated wall portions 78,80. In the illustrated embodiment, the leading edge 134 of the first perforated annular wall 78 may be connected to the inner surface of the outer wall 136 of the head end region 34. However, as shown in FIG. 9B, the front edge 134 of the first perforated annular wall 78 may not be connected to the outer wall 136 of the head end region 34. Further, in certain embodiments, the leading edge 134 of the first perforated annular wall 78 may be centered radially in the annular passage 40 through which the compressed air 38 flows into the head end region 34. As a result, an annular gap may be formed with respect to the air flow around the perforated turning blade 70.

  FIG. 9C shows a partial cross-sectional profile of the perforated turning vane 70 consistent with the airflow rectifier 50 shown in FIGS. Specifically, the illustrated perforated turning blade 70 includes a curved perforated annular wall 138. In the illustrated embodiment, the curved perforated annular wall 138 is concave shaped toward the central longitudinal axis 46 of the head end region 34. However, in other embodiments, the curved perforated annular wall 138 may instead be slightly convex. Further, in certain embodiments, the perforated turning vane 70 may include multiple wall portions with varying degrees of curvature (eg, C-shaped, U-shaped, J-shaped, S-shaped, etc.). In the illustrated embodiment, the leading edge 140 of the curved perforated annular wall 138 may be connected to the outer wall 136 of the head end region 34. However, as shown in FIG. 9D, the leading edge 140 of the curved perforated annular wall 138 may not be connected to the outer wall 136 of the head end region 34. Further, in certain embodiments, the leading edge 140 of the curved perforated annular wall 138 may be centered radially within the annular passage 40 through which the compressed air 38 flows into the head end region 34. Again, this can create an annular gap for the air flow around the perforated turning vane 70.

  However, these straight and curved cross sections are only some of the types of cross sections that may be used for perforated turning vanes 70. Further, a more complicated shape may be used. For example, FIG. 9E shows a partial cross-sectional profile for an L-shaped perforated turning blade 70. As shown in the figure, the perforated turning blade 70 is connected to a first perforated wall 142 that converges linearly toward the longitudinal axis 46 at the center of the head end region 34, and the first perforated wall 142. Alternatively, a second perforated wall 144 that converges linearly toward the central longitudinal axis 46 may be provided. However, the second perforated wall 144 faces rearward toward the partition plate 126 and forms an L-shaped portion between the first perforated wall 142 and the second perforated wall 144. In some embodiments, the shape between the first perforated wall 142 and the second perforated wall 144 may be generally triangular, but the first and second perforated walls 142, 144 are fully It does not have to be a straight line. Rather, the first and second perforated walls 142 and 144 are curved, but may still be in a state where a substantially triangular shape is formed between them. As described above with reference to FIGS. 9A-9D, the leading edge 146 of the perforated turning vane 70 may or may not be connected to the outer wall 136 of the head end region 34.

  FIG. 9F shows a partial cross-sectional profile for the hook-shaped perforated turning blade 70. As shown in the figure, the perforated turning blade 70 is connected to the first perforated wall 148 that linearly converges toward the central longitudinal axis 46 of the head end region 34, and the first perforated wall 148. The second perforated wall 150 may also be provided that converges linearly toward the central longitudinal axis 46. However, the second perforated wall 150 faces rearward toward the partition plate 126. Further, the air flow rectifier 50 may include a third perforated wall 152. The third perforated wall 152 is connected to the second perforated wall 150 but diverges away from the central longitudinal axis 46 while facing rearward toward the outer wall 136 of the head end region 34. A hook-shaped portion is formed between the first perforated wall 148, the second perforated wall 150, and the third perforated wall 152. In some embodiments, the shape between the first perforated wall 148, the second perforated wall 150, and the third perforated wall 152 may be substantially rectangular, but the first, second, and The third perforated walls 148, 150, 152 may not be completely straight. Rather, the first, second, and third perforated walls 148, 150, 152 may be curved but still have a generally rectangular shape formed therebetween. Again, as described above with respect to FIGS. 9A-9D, the leading edge 154 of the perforated turning vane 70 may or may not be connected to the outer wall 136 of the head end region 34.

  9G and 9H show two other partial cross-sectional profiles that are somewhat similar to the perforated turning vane 70. For example, FIG. 9G shows a partial cross-sectional profile of a perforated turning vane 70 with a perforated wall 156 with a 3/4 torus 158. Furthermore, other amounts of perforated walls 156 (eg, at least 50, 60, 70, 80, or 90% of the circumference) may be used. The perforated wall 156 is thus rounded rearward toward itself in a generally annular manner. Similarly, in FIG. 9H, a partial cross section of a perforated turning vane 70 comprising a perforated wall 160 with a curved trailing edge 162 facing rearward toward an annular passage 40 through which compressed air 38 flows into the head end region 34. Indicates a profile. For each of these embodiments, the particular shape of the cross-sectional profile of the perforated turning vane 70 may vary. In general, however, the embodiment comprises a cross-sectional profile of a perforated turning vane 70 with the trailing edge of the curved perforated wall facing back towards the annular passage 40. Again, as described above with respect to FIGS. 9A-9D, the leading edges 164, 166 of the perforated turning vane 70 shown in FIGS. 9G and 9H may or may not be connected to the outer wall 136 of the head end region 34. It does not have to be.

  Each of the perforated turning vane 70 embodiments shown in FIGS. 9E-9H has certain features on the trailing edge that can directly prevent the flow of compressed air 38 from entering the air chamber 68 of the headend region 34 to some extent directly. Sharing. For example, FIG. 10 is a perspective view of a portion of an exemplary embodiment of a perforated turning vane 70. Specifically, the perforated turning vane 70 shown in FIG. 10 is the perforated turning vane 70 of FIG. 9H, and has a curved shape that faces rearward toward the annular passage 40 through which the compressed air 38 flows into the head end region 34. A trailing edge 162 is provided. As the compressed air 38 enters the air chamber 68 of the head end region 34, the curved trailing edge 162 may substantially impede the flow of the compressed air 38. To alleviate this to some extent, the trailing edge 162 may be provided with a “castle stance” or “zigzag” design. This design includes a cut out portion 168 at the trailing edge 162. In some embodiments, the cutout 168 may be rectangular, but other cutout shapes (eg, triangles, circles, etc.) may be used. The cut out portion 168 may prevent the full velocity of the compressed air 38 from occurring at the trailing edge 162.

  Conversely, certain embodiments of the perforated turning vane 70 described in FIGS. 9A-9H should have a trailing edge that directly prevents the flow of compressed air 38 from entering the air chamber 68 of the headend region 34 to some extent. Not in. For example, the embodiment of the perforated turning vane 70 shown in FIGS. 9A to 9D has a cross-sectional profile that gradually sends the compressed air 38 back through the air chamber 68. Thus, the embodiment shown in FIGS. 9A-9D may use a single wall instead of a perforated wall in some embodiments. With a single wall, the compressed air 38 may not be able to be sent through the wall of the guide vane 70, but the single wall will still send the compressed air 38 toward the central longitudinal axis 46 of the head end region 34. As a result, the air distribution to the fuel nozzle 12 is made uniform. Also, in embodiments using perforations, the size, number and distribution of perforations may be varied.

  The airflow rectifier 50 embodiments described herein may be beneficial in a number of ways. In particular, since the air flow rectifier 50 creates a more uniform distribution of the compressed air 38 between the fuel nozzles 12, a uniform static pressure field likewise exists around the air inlet of the fuel nozzle 12. Furthermore, the uniform static pressure allows a balanced air mass flow through all the fuel nozzles 12, thus facilitating uniform air and fuel mixing. Further, since each fuel nozzle 12 receives a substantially similar amount of air flow, a single fuel nozzle 12 design may be used, resulting in a reduction in hardware or initial cost. Furthermore, emissions may be improved because the air and fuel mixture is more constant. Another benefit may be that the air profile at the fuel nozzle 12 is more uniform. As a result, the flame holding performance of the fuel nozzle 12 can be improved. In particular, because the air profile at the fuel nozzle 12 is more uniform, it is unlikely that a zone with reduced speed will occur. With such a zone, there is a possibility that the flame is fixed inside the fuel nozzle 12 and destroys the hardware.

  The description herein uses examples to disclose the invention, including the best mode, and to make and use, for example, any apparatus or system that enables those skilled in the art to practice the invention. Any way you can do it. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples have structural elements that do not differ from the literal wording of the claim, or include equivalent structural elements that are insubstantial to the literal wording of the claim. It is intended to be within the scope of the claims.

Claims (9)

A system Ru comprising a turbine engine (10), a combustor provided in the turbine engine (10) (16),
A combustion chamber (52);
A liner (44) provided around the combustion chamber (52);
A sleeve (42) provided around the liner (44);
An air supply path (38) between the liner (44) and the sleeve (42);
An air chamber (68);
A partition plate (126) provided between the combustion chamber (52) and the air chamber (68) in the axial direction with respect to the longitudinal axis of the combustor;
A fuel nozzle (12) extending through the partition plate (126) having an air inlet in the air chamber (68) and an outlet in the combustion chamber (52);
An air chamber (68) to place air flow rectifiers along the air supply path of the air chamber (68) (38) (50), radially overlapping the air supply path (38) about the longitudinal axis An air flow rectifier (50) comprising a first perforated turning wall (70) extending circumferentially at a position;
So that the first effective turning wall (70) passes the first portion (84) of the airflow flowing through the air supply path (38) from the combustion chamber (52) in the upstream direction. An air supply path having a first plurality of openings configured and having a first effective turning wall (70) inclined inward toward the longitudinal axis upstream from the air supply path (38). the second portion of the air flow from (38) to (88) deflect inwardly towards the central portion of the air chamber (68), the system. The perforated turning wall (70) comprises a first perforated annular wall (72) disposed about the longitudinal axis (46) of the combustor (16), the first perforated annular wall (72) The system of any preceding claim, wherein the diameter decreases upstream from the combustion chamber (52) along the longitudinal axis (46). The first perforated annular wall (72) comprises one or more perforated conical wall provided around the longitudinal axis (46) (78,80,142,144,148,150,152), claim 2. The system according to 2.   The system of claim 2, wherein the first perforated annular wall (72) bends convexly or concavely along the longitudinal axis (46).   The air flow rectifier (50) comprises a perforated cylinder (82) having a second perforated annular wall disposed about the longitudinal axis (46) of the combustor (16), the second perforated annular wall. The system according to claim 2, wherein has a substantially constant diameter along the longitudinal axis.   The system of claim 5, wherein the first and second perforated annular walls are concentric with each other. The fuel nozzle (12) comprises an intake flow rectifier at the air inlet, the intake flow rectifier comprises nozzle perforations (48), and the intake flow rectifier is separate from the air flow rectifier (50). 7. The system according to any one of items 6.   The system of any preceding claim, wherein the air flow rectifier (50) is configured to provide a uniform air flow to the air inlet of the fuel nozzle (12). A plurality of fuel nozzles (12) extending through the divider plate (126) is provided, and the airflow rectifier (50) is configured to evenly distribute the airflow among the plurality of fuel nozzles (12). The system according to any one of claims 1 to 8.

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